CN1273813C - Full machine ground load on site calibration test method and its device - Google Patents
Full machine ground load on site calibration test method and its device Download PDFInfo
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- CN1273813C CN1273813C CN 02158959 CN02158959A CN1273813C CN 1273813 C CN1273813 C CN 1273813C CN 02158959 CN02158959 CN 02158959 CN 02158959 A CN02158959 A CN 02158959A CN 1273813 C CN1273813 C CN 1273813C
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Abstract
The present invention discloses an on-line marked test method of a wing loading online, and a special device using the test method in the stopping state of an airplane. The special device uses a support frame and a landing frame as support points. Thus, the airplane uses a strain sensor device to make loadings applied to a selected cross section, and to record loading number values when the airplane maintains a horizontal state. The method and the special device realize the on-line marking of the airplane wing online. Thus, the present invention not only guarantees the truth of received loadings, but also guarantees the measuring precision and the marking accuracy of the loadings. The present invention provides references for establishing a wing loading equation, fatigue lives and simulation tests.
Description
Technical field
The present invention relates to a kind of aircraft wing load calibration test method.
Background technology
Aircraft wing is as the vitals under the state of flight, need it should be in light weight, but it is safe in utilization again, therefore, understand that its force-bearing situation and serviceable life are the problems that people are concerned about always, but past when wing is carried out load test carries out after all wing being removed from aircraft, such test had not both guaranteed the authenticity of stand under load, did not guarantee the precision of load measurement and demarcation yet.
The present inventor is at the deficiencies in the prior art; carry out discovering with great concentration, under the condition that wing, empennage are not dismantled, carried out on-the-spot load and apply and demarcate, promptly can guarantee the safety of aircraft; can protect the authenticity of stand under load and the precision of load calibration again, so finished the present invention.
Summary of the invention
The object of the invention provides a kind of ground experimental Study on Field Calibration method of complete airborne lotus test of attaching most importance to wing, empennage, solves complete airborne lotus (comprising moment M, shearing Q and the torque T) on-line proving that present domestic aircraft attaches most importance to wing, empennage and the difficult problem of actual measurement with this.
A further object of the present invention provides a kind of device of realizing the ground experimental Study on Field Calibration method of described complete airborne lotus test.
By the result data that the test of strain transducer load calibration obtains, set up load equation, measure so that carry out aerial loading spectrum.And then measured aircraft exactly and in flight course He under the ground motion state, acted on structural external applied load time histories such as wing, empennage.
Specifically, carrying out aircraft wing load field calibration when test, aircraft is kept demarcating under the stopped status, it is characterized in that: it is to carry out according to following step under the condition that undercarriage is not dismantled:
(1) demarcate coordinate system, true origin is the fuselage construction horizontal line and the intersection point of 0 bit line (behind the head 1.0 meters), and X-axis overlaps with the fuselage construction horizontal line, and backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, Z axle sensing left wing and X, Y-axis formation right-handed system;
(2) wing when test with aircraft master lifting jack aircraft jack-up, with the protection carriage and the nose-gear that are added in the fuselage place is fulcrum, make the main landing gear built on stilts, central wing keeps horizontality, and aircraft system horizontal line and ground angle are determined the sectional position of load 2 °～4 ° (bowing), the load sectional tool is representative and guarantee that the installation device of sensor that can count record load is arranged, when when a wing loads, the wing will add balancing load (total outer EMx=0 that carries) in addition, and the record load value;
When (3) horizontal tail was tested, undercarriage landed, and is tight with the weight retaining before the gear tyre, with carriage aircraft held, and determines the load sectional position, is carried in the load section perpendicular to the horizontal tail string, and connect sensor device, and write down loaded load,
When (4) vertical fin was tested, undercarriage landed, and tight with the weight retaining before the gear tyre, the vertical fin side direction loads, and to the device of a balance lateral loading moment of aircraft, determines to load behind the load sectional position, connects sensor device, and the record loaded load.
When carrying out described aircraft wing load field calibration test method, all points of load are applied to rib and spar junction on the aerofoil, and its contact area is not less than 120mm * 160mm.
Preferably, when carrying out described aircraft wing load field calibration test method, utilize suitable loading lifting jack or load spindle arrangement wing is loaded, force transducer is placed on main lifting jack upper end, withstand in the middle of the loading lever, the two ends of lever are connected with two clamps on the wing, the section that clamp is determined at wing, three loading positions in wing front and rear beam and front and rear beam center are by change lever positions and lifting jack position and vertex position realization loading requirement.
And, equally preferably, when carrying out described aircraft wing load field calibration test method, left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press a counterweight above, connect sensor with the manual pulley device, on connect combining leverage, connecing versatilely down, rail loads.
Simultaneously, when vertical fin loads, the device of giving a balance lateral loading moment of aircraft is the upright side direction column in the main load frame right side at airframe airframe afterbody, column is pressed in ground with counterweight, adorn an identical wooden unit of main load frame profile with the airframe afterbody in column upper end and the identical place of main load frame height of airframe afterbody, test main load frame preceding and aircraft airframe afterbody is close to.
When vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end links to each other with the loading lever with sensor by wire rope, and the other end utilizes pulley guiding and manual pulley device to join, and the manual pulley device other end and crane are fixed, utilize the manual pulley device to load, and the record load value.
In addition, the present invention also provides a kind of isolated plant of realizing described aircraft wing load field calibration test method, it is characterized in that: the sensor device of aircraft is that force transducer is placed on the lifting jack upper end, withstand on and load in the middle of the lever, the two ends of lever are connected with two clamps on the wing, and clamp is stuck in the definite section of wing, three loading positions of wing front and rear beam and front and rear beam center by change lever positions and lifting jack position and vertex position realization loading requirement.
Preferably, the horizontal tail charger is that left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects ground with a rail versatilely with lever again, presses a counterweight above, with manual pulley device connection sensor, on connect combining leverage, down connecing versatilely, rail loads.
Equally preferably, the vertical fin charger is to block with clamp at selected section, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end links to each other with the loading lever with sensor by wire rope, and the other end utilizes pulley guiding and manual pulley device to join, and the manual pulley device other end and crane are fixed, utilize the manual pulley device to load, and the record load value.
Because the present invention carries out under the condition that wing is not dismantled, both guaranteed the safety of aircraft, the authenticity of wing stand under load and the precision of load calibration have been guaranteed again, set up load equation by the test of strain transducer load calibration, also just can measure aircraft acts on wing under state of flight external applied load time history exactly, decide the mechanics basis of longevity and simulation test loading as fatigue.
Description of drawings
Fig. 1 is the load(ing) point location drawing.
Fig. 2 is a horizontal tail load(ing) point synoptic diagram.
Fig. 3 is a vertical fin load(ing) point synoptic diagram.
Fig. 4 is the aircraft floor status of support.
Fig. 5 is that wing is demarcated the loading synoptic diagram.
Fig. 6 is that horizontal tail is demarcated the loading synoptic diagram.
Fig. 7 is that vertical fin is demarcated the loading synoptic diagram.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples:
At first selected coordinate system, coordinate is that full machine coordinate system true origin is the intersection point of fuselage construction horizontal line and 0 bit line (behind the head 1.0 meters), and X-axis overlaps with the fuselage construction horizontal line, backward for just, upwards for just, the Z axle points to left wing and X, Y-axis formation right-handed system to Y-axis in the aircraft plane of symmetry.
1 wing load calibration
1.1 load measurement tangent plane
The I tangent plane is the outer 400 millimeters places of right flank 12 ribs; The II tangent plane is the outer 250 millimeters places of right flank 7 ribs;
The III tangent plane is the outer 400 millimeters places of right flank 2 ribs; The IV tangent plane is the outer 400 millimeters places of left wing's 2 ribs.
1.2 aircraft state
Main landing gear built on stilts during the wing test, central wing keeps horizontality, and aircraft system horizontal line and ground angle are approximately 3 °.
1.3 test situation and load
Fig. 1 is seen in the load(ing) point position, and test situation and magnitude of load see Table 1.
The table 1 wing test load and the pressure heart
| Load type | Sequence number | I tangent plane (12 ribs are outer) | II, III, IV tangent plane (outside 7 ribs, 2 ribs are outer) | ||||
| X(m) | Z(m) | P(kN) | X(m) | Z(m) | P(kN) | ||
| Demarcate load | 1 | 9.868 | -11.00 | 25 | 9.565 | -8.76 | 40 |
| 2 | 9.929 | -11.45 | 30 | 9.620 | -9.16 | 50 | |
| 3 | 9.989 | -11.90 | 20 | 9.687 | -9.66 | 35 | |
| 4 | 10.577 | -11.00 | 25 | 10.456 | -8.76 | 40 | |
| 5 | 10.602 | -11.45 | 30 | 10.478 | -9.16 | 50 | |
| 6 | 10.626 | -11.90 | 20 | 10.505 | -9.66 | 35 | |
| 7 | 10.223 | -11.00 | 40 | 10.011 | -8.76 | 60 | |
| 8 | 10.265 | -11.45 | 40 | 10.049 | -9.16 | 60 | |
| 9 | 10.308 | -11.90 | 40 | 10.096 | -9.66 | 60 | |
| Check load | 1 | 10.171 | -11.417 | 40 | 9.918 | -9.075 | 60 |
| 2 | 10.353 | -11.417 | 40 | 10.164 | -9.075 | 60 | |
| 3 | 10.214 | -12.210 | 30 | 9.960 | -9.850 | 50 | |
| 4 | 10.460 | -12.210 | 30 | 10.269 | -9.850 | 50 | |
2 empennage load calibrations
2.1 load measurement tangent plane
Horizontal tail: the V tangent plane is right horizontal tail and fuselage interface outer 350;
Horizontal tail: the VI tangent plane is left horizontal tail and fuselage interface outer 350;
Vertical fin: the VII tangent plane is on vertical fin 1 rib 50.
2.2 aircraft state
Rise before the aircraft, led and land.Horizontal tail loads in horizontal tail string plane (outside 9 °) downward vertically, and the vertical fin side direction loads.
2.3 test situation and load
Test situation and magnitude of load see Table 2.
Fig. 2, Fig. 3 are seen in the load(ing) point position.
The table 2 empennage test load and the pressure heart
| Load type | Sequence number | Tailplane (left side) | Vertical tail | ||||
| X(m) | Z(m) | P(kN) | X(m) | Y(m) | P(kN) | ||
| Demarcate load | 1 | 21.890 | 1.948 | -9 | 20.803 | 3.390 | 10 |
| 2 | 22.009 | 2.343 | -9 | 21.974 | 3.790 | 10 | |
| 3 | 22.128 | 2.739 | -7 | 21.145 | 4.190 | 7 | |
| 4 | 22.705 | 1.948 | -9 | 21.902 | 3.390 | 10 | |
| 5 | 22.770 | 2.343 | -9 | 22.003 | 3.790 | 10 | |
| 6 | 22.836 | 2.739 | -7 | 22.103 | 4.190 | 7 | |
| 7 | 22.298 | 1.948 | -12 | 21.353 | 3.390 | 14 | |
| 8 | 22.390 | 2.343 | -12 | 21.488 | 3.790 | 14 | |
| 9 | 22.482 | 2.739 | -12 | 21.624 | 4.190 | 14 | |
| Check load | 1 | 22.230 | 2.091 | -12 | 21.276 | 3.600 | 14 |
| 2 | 22.433 | 2.091 | -12 | 21.572 | 3.600 | 14 | |
| 3 | 22.347 | 2.798 | -9 | 21.402 | 4.100 | 10 | |
| 4 | 22.644 | 2.798 | -9 | 21.785 | 4.100 | 10 | |
2.4 aerofoil load position and restriction
All points of load must be applied to the intersection point place of rib and spar on the aerofoil, and its contact area is not less than 120 * 160.
The each point load limit is as follows:
Wing 21 ribs-5kN
19 ribs-10kN
17 ribs-12kN
14 ribs-20kN
9,11 ribs-35kN
7 ribs-50kN
Horizontal tail 9 ribs are with interior each point 6kN, in addition to 12 rib each point 3kN.
Vertical fin 10 ribs are with interior each point 7kN, in addition to 13 rib each point 4kN.
3 test methods
3.1 wing is demarcated loading method
3.1.1 aircraft floor status of support
Aircraft jack-up, is fulcrum with 20 frame carriages and preceding with aircraft master lifting jack, makes the main landing gear built on stilts, makes central wing keep horizontality, and adds the protection carriage at fuselage 31 frame places, and aircraft can not roll when guaranteeing to load.Before play the most following of pillar and live with the column pad, and block in front with the assurance aircraft with block (or weight) and can not move forward.The angle on aircraft system horizontal line and ground is approximately 3 ° (bowing) and sees Fig. 4.
3.1.2 wing is demarcated loading method
Starboard wing with three secondary clamps (11 ribs, 15 ribs, 20 ribs) port wing second mate clamps (11 ribs, 15 ribs) when left and right sides wing loads with 11 ribs, 15 ribs, left-right symmetric loads, when starboard wing 15 ribs, when 20 ribs load, port wing adds balancing load (total outer ∑ MX=0 that carries).
Utilize the suitable loading lifting jack of aircraft or load spindle arrangement wing is loaded, force transducer is placed on main lifting jack upper end, withstands on to load in the middle of the lever, and the two ends of lever are connected with two clamps on the wing.Clamp by change lever positions and lifting jack position and vertex position realization loading requirement, is seen Fig. 1, Fig. 5 at three loading positions of wing front and rear beam and front and rear beam center.
3.1.2.1 demarcating, wing I tangent plane loads
Starboard wing 15 ribs, 20 ribs load, port wing 11 ribs, 15 ribs add balancing load, and port wing uses the hole that loads lever to link to each other with 11 rib clamp center pits, and other end fixed orifice links to each other with 15 rib clamp center pits, the middle part fixed orifice links to each other with very heavy summit, and the starboard wing lever connects and load sees Table 4.
Table 4 wing I tangent plane nominal data (in the table data unreceipted be the starboard wing data)
| Test situation | Position, 15 rib clamp hole | Load lever hole number | Position, 20 rib clamp hole | Load lever hole number | Hole, lifting jack position number | Thousand Ns of right flank load | Right load is pressed heart X | Right load is pressed heart Z | Thousand Ns of left wing's load |
| 1 | Before | 28 | Before | 29 | 30 | 25 | 9.868 | 11.000 | 30.02 |
| 2 | Before | 28 | Before | 29 | 31 | 30 | 9.929 | 11.450 | 37.50 |
| 3 | Before | 28 | Before | 29 | 32 | 20 | 9.989 | 11.900 | 25.98 |
| 4 | After | 33 | After | 34 | 35 | 25 | 10.577 | 11.000 | 30.02 |
| 5 | After | 33 | After | 34 | 36 | 30 | 10.602 | 11.450 | 37.50 |
| 6 | After | 33 | After | 34 | 37 | 20 | 10.626 | 11.900 | 25.98 |
| 7 | In | 38 | In | 39 | 40 | 40 | 10.223 | 11.000 | 48.03 |
| 8 | In | 38 | In | 39 | 41 | 40 | 10.265 | 11.450 | 50.00 |
| 9 | In | 38 | In | 39 | 42 | 40 | 10.308 | 11.900 | 51.97 |
| 10 | In | 43 | Before | 44 | 45 | 40 | 10.171 | 11.417 | 49.85 |
| 11 | In | 46 | After | 47 | 48 | 40 | 10.353 | 11.417 | 49.85 |
| 12 | Before | 49 | In | 50 | 51 | 30 | 10.214 | 12.210 | 39.98 |
| 13 | After | 52 | In | 53 | 54 | 30 | 10.460 | 12.210 | 39.98 |
3.1.2.2 wing II, III, IV tangent plane are demarcated and are loaded
Left and right sides wing loads in 11 ribs, 15 ribs symmetry, and lever connects and load sees Table 5.
Table 5: wing II, III, IV tangent plane nominal data
| Test situation | Position, 11 rib clamp hole | Load lever hole number | Position, 15 rib clamp hole | Load lever hole number | Hole, lifting jack position number | Thousand Ns of right flank load | Right load is pressed heart X | Right load is pressed heart Z |
| 1 | Before | 1 | Before | 2 | 3 | 40 | 9.565 | 8.760 |
| 2 | Before | 1 | Before | 2 | 4 | 50 | 9.620 | 9.160 |
| 3 | Before | 1 | Before | 2 | 5 | 35 | 9.687 | 9.660 |
| 4 | After | 6 | After | 7 | 8 | 40 | 10.456 | 8.760 |
| 5 | After | 6 | After | 7 | 9 | 50 | 10.478 | 9.160 |
| 6 | After | 6 | After | 7 | 10 | 35 | 10.505 | 9.660 |
| 7 | In | 11 | In | 12 | 13 | 60 | 10.011 | 8.760 |
| 8 | In | 11 | In | 12 | 14 | 60 | 10.049 | 9.160 |
| 9 | In | 11 | In | 12 | 15 | 60 | 10.096 | 9.660 |
| 10 | In | 16 | Before | 17 | 18 | 60 | 9.918 | 9.075 |
| 11 | In | 19 | After | 20 | 21 | 60 | 10.164 | 9.075 |
| 12 | Before | 22 | In | 23 | 24 | 50 | 9.960 | 9.850 |
| 13 | After | 25 | In | 26 | 27 | 50 | 10.269 | 9.850 |
3.1.3 tailplane is demarcated loading method
3.1.3.1 aircraft state
Aircraft keeps stopped status, nose-gear, and main landing gear is tight with the catch retaining, with 20 frame carriages aircraft is held, and adds counterweight (or with fuselage 31 frame carriages) at the fuselage front deck and comes balance Z to moment
3.1.3.2 demarcation loading method
Left and right sides horizontal tail is at 3 ribs, clamp is equipped with at 10 rib places, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is with a lever and 3 ribs, 10 rib clamps connect, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press 4～5 tons of counterweights above, connect sensor with the manual pulley device, on connect the combining leverage (see figure 6), down connect versatilely that rail loads, Fig. 2 is seen in the load(ing) point position, load sees Table 2, installation form is seen Fig. 6, and 9 ° at the tailplane upper counterangle guarantees during loading that loading direction is vertical with horizontal tail string plane.
3.1.3.3 lever connects and magnitude of load
The horizontal tail lever connects and magnitude of load sees Table 6
The lever of table 6 horizontal tail: V, VI tangent plane connects and load data
| Test situation | Position, 3 rib clamp hole | Load lever hole number | Position, 10 rib clamp hole | Load lever hole number | Lever center pit number | Combining leverage hole number | The lever web member is long | Load coordinate X value | Always add thousand Ns of load |
| 1 | Before | 1 | Before | 2 | 3 | 1 | 989 | 21.890 | 17.78 |
| 2 | Before | 1 | Before | 2 | 4 | 2 | 1052 | 22.009 | 17.78 |
| 3 | Before | 1 | Before | 2 | 5 | 3 | 1115 | 22.128 | 13.83 |
| 4 | After | 11 | After | 12 | 13 | 1 | 989 | 22.705 | 17.78 |
| 5 | After | 11 | After | 12 | 14 | 2 | 1052 | 22.770 | 17.78 |
| 6 | After | 11 | After | 12 | 15 | 3 | 1115 | 22.836 | 13.83 |
| 7 | In | 6 | In | 7 | 8 | 1 | 989 | 22.298 | 23.70 |
| 8 | In | 6 | In | 7 | 9 | 2 | 1052 | 22.390 | 23.70 |
| 9 | In | 6 | In | 7 | 10 | 3 | 1115 | 22.482 | 23.70 |
| 10 | In | 6 | Before | 16 | 17 | 4 | 1011 | 22.230 | 23.70 |
| 11 | In | 6 | After | 18 | 19 | 4 | 1011 | 22.433 | 23.79 |
| 12 | Before | 6 | In | 20 | 21 | 5 | 1125 | 22.347 | 17.78 |
| 13 | After | 22 | In | 23 | 24 | 5 | 1125 | 22.644 | 17.78 |
Annotate: tangent plane web member length counts 3 ribs, 390,10 ribs, 430 unit millimeters.
3.1.4 vertical tail is demarcated loading method
3.1.4.1 aircraft state
Aircraft state is identical when demarcating loading with tailplane
3.1.4.2 the side direction support of aircraft
What the vertical fin demarcation added is that Z is to load, thereby to aircraft can produce Y to X to moment, must give the certain constraint of aircraft, upright side direction column that 3m is high on airframe 43 frame right sides, column is pressed in ground with counterweight, adorn in column upper end and the identical place of 43 frame height one with the identical wooden unit of 43 frame profiles, preceding and aircraft 43 frames of test are close to.
3.1.4.3 demarcation loading method
Vertical fin 5 ribs, 10 ribs block with the loading clamp, utilize one to load the load that each situation is implemented in the lever change position, magnitude of load sees Table 2, and Fig. 3 is seen in the load(ing) point position, utilize the cantilever pulley of 15 tons of cranes, an end links to each other with the loading lever with sensor by wire rope.The other end utilizes pulley guiding and manual pulley device to join, and the manual pulley device other end and crane are fixed, and utilize the manual pulley device to load, and see Fig. 7.
3.1.4.4 lever connects and magnitude of load
The vertical fin lever connects and magnitude of load sees Table 7
Table 7: vertical fin: the lever of VII tangent plane connects and load data
| Test situation | Position, 5 rib clamp hole | Load lever hole number | Position, 10 rib clamp hole | Load lever hole number | Lever center pit number | Thousand Ns of side loads | Side load is pressed heart X | Side load is pressed heart Y |
| 1 | Before | 1 | Before | 2 | 3 | 10 | 20.803 | 3.390 |
| 2 | Before | 1 | Before | 2 | 4 | 10 | 20.974 | 3.790 |
| 3 | Before | 1 | Before | 2 | 5 | 7 | 21.145 | 4.190 |
| 4 | After | 6 | After | 7 | 8 | 10 | 21.902 | 3.390 |
| 5 | After | 6 | After | 7 | 9 | 10 | 22.003 | 3.790 |
| 6 | After | 6 | After | 7 | 10 | 7 | 22.103 | 4.190 |
| 7 | In | 11 | In | 12 | 13 | 14 | 21.353 | 3.390 |
| 8 | In | 11 | In | 12 | 14 | 14 | 21.488 | 3.790 |
| 9 | In | 11 | In | 12 | 15 | 14 | 21.624 | 4.190 |
| 10 | In | 11 | Before | 16 | 17 | 14 | 21.276 | 3.600 |
| 11 | In | 11 | After | 18 | 19 | 14 | 21.572 | 3.600 |
| 12 | Before | 1 | In | 20 | 21 | 10 | 21.402 | 4.100 |
| 13 | After | 11 | In | 22 | 23 | 10 | 21.785 | 4.100 |
In addition, the present invention is not only applicable to aircraft wing, for the structure of other similar wing, so long as under the condition of not dismantling, with sensor device test machine wing load, all belong to protection scope of the present invention.
Claims (12)
1, a kind of full machine landing load experimental Study on Field Calibration method, it keeps demarcating under the stopped status at aircraft, and it is characterized in that: it is to carry out according to following step under the condition that undercarriage is not dismantled:
(1) demarcate coordinate system, true origin is fuselage construction horizontal line and 0 bit line, i.e. the intersection point at 1.0 meters behind the head, and X-axis overlaps with the fuselage construction horizontal line, and backward for just, Y-axis makes progress in the aircraft plane of symmetry to just, Z axle sensing left wing and X, Y-axis formation right-handed system;
(2) wing when test with aircraft master lifting jack aircraft jack-up, with the protection carriage and the nose-gear that are added in the fuselage place is fulcrum, make the main landing gear built on stilts, central wing keeps horizontality, and aircraft system horizontal line and ground angle are determined the sectional position of load at 2 °～4 °, the load sectional tool is representative and guarantee that the installation device of sensor that can count record load is arranged, when when a wing loads, the wing will add balancing load in addition, and the record load value;
When (3) horizontal tail was tested, undercarriage landed, and is tight with the weight retaining before the gear tyre, with carriage aircraft held, and determines the load sectional position, load perpendicular to the horizontal tail string, and at the load section, connection sensor device, and record loaded load;
When (4) vertical fin was tested, undercarriage landed, and tight with the weight retaining before the gear tyre, the vertical fin side direction loads, and to the device of a balance lateral loading moment of aircraft, determines to load behind the load sectional position, connects sensor device, and the record loaded load.
2, full machine landing load experimental Study on Field Calibration method according to claim 1, it is characterized in that: all points of load are applied to rib and spar junction on the aerofoil, and its contact area is not less than 120mm * 160mm.
3, full machine landing load experimental Study on Field Calibration method according to claim 1 and 2, it is characterized in that: utilize the suitable loading lifting jack of aircraft or load spindle arrangement wing is loaded, force transducer is placed on main lifting jack upper end, withstand on and load in the middle of the lever, the two ends of lever are connected with two clamps on the wing, the section that clamp is determined at wing, three loading positions in wing front and rear beam and front and rear beam center are by change lever positions and lifting jack position and vertex position realization loading requirement.
4, full machine landing load experimental Study on Field Calibration method according to claim 1 and 2, it is characterized in that: left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three to load the hole at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press a counterweight above, connect sensor with the manual pulley device, on connect combining leverage, down connecing versatilely, rail loads.
5, full machine landing load experimental Study on Field Calibration method according to claim 3, it is characterized in that: left and right sides horizontal tail is equipped with clamp in the load cross section of determining, each clamp has three loadings at the front and rear beam of horizontal tail and the center of front and rear beam, each load condition is connected with the clamp of a lever and selected section, left and right sides horizontal tail connects with a lever again, ground is with a rail versatilely, press a counterweight above, connect sensor with the manual pulley device, on connect combining leverage, down connecing versatilely, rail loads.
6, full machine landing load experimental Study on Field Calibration method according to claim 1 and 2, it is characterized in that: when vertical fin loads, the device of giving a balance lateral loading moment of aircraft is the upright side direction column in the main load frame right side at the airframe afterbody, column is pressed in ground with counterweight, adorn an identical wooden unit of main load frame profile with the airframe afterbody in column upper end and the identical place of main load frame height of airframe afterbody, test main load frame preceding and aircraft airframe afterbody is close to.
7, full machine landing load experimental Study on Field Calibration method according to claim 3, it is characterized in that: the device of giving a balance lateral loading moment of aircraft when vertical fin loads is the upright side direction column in the main load frame right side at airframe airframe afterbody, column is pressed in ground with counterweight, adorn an identical wooden unit of main load frame profile with the airframe afterbody in column upper end and the identical place of main load frame height of airframe afterbody, test main load frame preceding and aircraft airframe afterbody is close to.
8, full machine landing load experimental Study on Field Calibration method according to claim 5, it is characterized in that: the device of giving a balance lateral loading moment of aircraft when vertical fin loads is the upright side direction column in the main load frame right side at airframe airframe afterbody, column is pressed in ground with counterweight, adorn an identical wooden unit of main load frame profile with the airframe afterbody in column upper end and the identical place of main load frame height of airframe afterbody, test main load frame preceding and aircraft airframe afterbody is close to.
9, full machine landing load experimental Study on Field Calibration method according to claim 1 and 2, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and manual pulley device to join, the manual pulley device other end and crane are fixed, utilize the manual pulley device to load, and the record load value.
10, full machine landing load experimental Study on Field Calibration method according to claim 3, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and manual pulley device to join, the manual pulley device other end and crane are fixed, utilize the manual pulley device to load, and the record load value.
11, full machine landing load experimental Study on Field Calibration method according to claim 5, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and manual pulley device to join, the manual pulley device other end and crane are fixed, utilize the manual pulley device to load, and the record load value.
12, full machine landing load experimental Study on Field Calibration method according to claim 8, it is characterized in that: when vertical fin loads, selected section blocks with clamp, utilize one to load the load that each situation is implemented in the lever change position, utilize the cantilever pulley of a crane, one end links to each other with the loading lever with sensor by wire rope, the other end utilizes pulley guiding and manual pulley device to join, the manual pulley device other end and crane are fixed, utilize the manual pulley device to load, and the record load value.
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| Application Number | Priority Date | Filing Date | Title |
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| CN 02158959 CN1273813C (en) | 2002-12-31 | 2002-12-31 | Full machine ground load on site calibration test method and its device |
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| CN 02158959 CN1273813C (en) | 2002-12-31 | 2002-12-31 | Full machine ground load on site calibration test method and its device |
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| CN1514213A CN1514213A (en) | 2004-07-21 |
| CN1273813C true CN1273813C (en) | 2006-09-06 |
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| CN 02158959 Expired - Fee Related CN1273813C (en) | 2002-12-31 | 2002-12-31 | Full machine ground load on site calibration test method and its device |
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